GB846358A - Combination engine starter and accessory drive apparatus - Google Patents
Combination engine starter and accessory drive apparatusInfo
- Publication number
- GB846358A GB846358A GB18701/58A GB1870158A GB846358A GB 846358 A GB846358 A GB 846358A GB 18701/58 A GB18701/58 A GB 18701/58A GB 1870158 A GB1870158 A GB 1870158A GB 846358 A GB846358 A GB 846358A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shaft
- turbine
- speed
- conduit
- chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
- F02C7/275—Mechanical drives
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
- F02C7/275—Mechanical drives
- F02C7/277—Mechanical drives the starter being a separate turbine
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H2700/00—Transmission housings and mounting of transmission components therein; Cooling; Lubrication; Flexible suspensions, e.g. floating frames
- F16H2700/02—Transmissions, specially for working vehicles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H3/00—Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion
- F16H3/44—Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion using gears having orbital motion
- F16H3/72—Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion using gears having orbital motion with a secondary drive, e.g. regulating motor, in order to vary speed continuously
- F16H3/724—Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion using gears having orbital motion with a secondary drive, e.g. regulating motor, in order to vary speed continuously using external powered electric machines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T74/00—Machine element or mechanism
- Y10T74/19—Gearing
- Y10T74/19023—Plural power paths to and/or from gearing
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Retarders (AREA)
Abstract
846,358. Engine turning-gear. GARRETT CORPORATION. June 11, 1958 [June 12, 1957], No. 18701/58. Class 7(5). [Also in Group XXVI] A combination engine starter and accessory drive apparatus for installation in an aircraft and which can alternatively deliver power to a main shaft 15, Figs. 1 and 6, for starting a jet engine connected thereto or receive power from the main shaft to drive a generator 12, comprises a gear train 14 connected to the shaft 15, an air turbine 13 directly connected to the gear train to provide continuous driving power thereto when the shaft 15 is both receiving and delivering power, an accessory shaft 42 to which the generator 12 is connected, the shaft 42 being directly connected with the gear train and driven both when the shaft 15 is delivering and receiving power, and speed sensitive means controlling means for modifying the operation of the gear train so that the shaft 15 receives a substantial share of the power output of the turbine 13 when the speed of the shaft is below a predetermined speed and the load on the shaft 42 is shared between the turbine 13 and the shaft 15 after the shaft 15 attains a predetermined speed. As shown, the gear train 14 comprises an epicyclic differential gear including a ring gear assembly 22 and two sets of planet gears 28, 27 and 26, 38 mounted on stub shafts 30 extending from a rotatable spider 21 mounted on bearings 43 and to which is splined the shaft 15. Air is supplied to the turbine wheel 36 through a conduit 49 via an annular inlet passage 50 and a nozzle 54, the speed of the turbine being varied by regulating the flow of air through the turbine by adjustable vanes 57 pivotably mounted in the nozzle and connected to a lever 61 operated by a control system 63 including a combination servo and hydraulic actuator 70 which is supplied by fluid under pressure from a gear pump 64 driven from the generator shaft 42 and which is pneumatically controlled by a speed sensing governor 71 also driven from the shaft 42. In operation, the governor 71 is arranged to produce a predetermined constant speed of the generator and any change thereof is compensated by the governor transmitting a signal to the actuator 70 causing the latter to adjust the vanes 57 to increase or decrease the speed of the turbine 13. For starting the engine, the ring gear assembly 22 is held stationary by a brake device 73 actuated by an annular piston 80 provided in an annular chamber 79 to which fluid under pressure is supplied, so that rotary motion transmitted by the turbine 13 to the planets 28, 27 is imparted to the shaft 15 through the spider 21, the generator shaft 42 being simultaneously driven by the planets 38. An air regulator and shut-off valve 82 are connected to the conduit 49 and a conduit 84 connected to the conduit 49 and comprising a pressure regulator 83 is connected to a starting selector valve 85, which includes a spool 86 connected with a wall 87 spring loaded on one side and having a chamber 94 on the other side to which air is supplied from the conduit 84 through a branch pipe 90, the air supply being controlled by a speed sensor 91 driven from the shaft 42 which permits air to bleed from the passage 90 to atmosphere until the shaft 42 attains a predetermined speed. The conduit 84 leads from the valve 85 to the piston chamber 79 of the brake 73. When the chamber 94 is not pressurized the spool 86 is urged by the spring 88 to the position shown in Fig. 6 and fluid pressure is supplied to operate the brake 73 when the engine is started as described above. When the shaft 15 is rotated at a speed sufficient to start the engine the speed sensor 91 prevents air being bled from the passage 90 whereupon the chamber 94 is pressurized and the spool 86 is moved to a second position in which a conduit 95 branching from the conduit 84 communicates with the speed governor 71, the chamber 79 being simultaneously vented and the brake 73 released. The switch for loading the generator is then actuated and the constant speed drive mechanism operates normally. In a modification of the control system, Fig. 7, the speed of the turbine 102 is controlled by a variable exit nozzle 104 in which a movable element 105 moves in response to fluid pressure in a chamber 106 to vary the flow of exhaust fluid through the passage 101. Variable pressure is supplied to the chamber 106 through a passage 107 connected to the exhaust passage 101, a bleed outlet 108 to atmosphere from the passage 107 being controlled by a valve 110 controlled by the governor 71 through the conduit 95 which extends to an actuator 109. To prevent the generator or the turbine from overspeeding both control systems are provided with a speed sensor 111 driven by the shaft 42 and with an overspeed sensing device 114 in the turbine shaft which are both connected through a conduit 112 to the valve 82. If either the generator or the turbine overspeeds the respective speed sensor 111 or 114 operates to vent the conduit 112 to atmosphere and the valve 82 interrupts fluid flow to the turbine. In a modified form of the invention, Fig. 4, the differential gearing 115 consists of two sets of planets 116, 117 rotatably,mounted on a spider 118 secured to the shaft 15, the set 116 being driven from a torsion shaft 121 connected to the turbine wheel 36 and the set 117 being driven from the shaft 42 and both sets meshing with the ring gear assembly 22. A brake mechanism 125 is axially offset from the ring gear assembly 22 and is splined to a conically shaped ring plate 127 which is in turn splined to the assembly 22, the brake being actuated by an annular piston 134 in a chamber 135 to which fluid under pressure is supplied. Means for utilising the residual energy in the turbine exhaust include (a) conducting the exhaust to the tail pipe of the aircraft main engine; (b) conducting the exhaust to the intermediate stage of the compressor of the main engine; (c) discharging the exhaust to atmosphere through a jet nozzle. Specifications 710,095, 760,656 and 837,833 are referred to.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US665147A US2908189A (en) | 1957-06-12 | 1957-06-12 | Combination engine starter and constant speed drive |
Publications (1)
Publication Number | Publication Date |
---|---|
GB846358A true GB846358A (en) | 1960-08-31 |
Family
ID=24668919
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB18701/58A Expired GB846358A (en) | 1957-06-12 | 1958-06-11 | Combination engine starter and accessory drive apparatus |
Country Status (4)
Country | Link |
---|---|
US (1) | US2908189A (en) |
DE (1) | DE1401273B1 (en) |
FR (1) | FR1208466A (en) |
GB (1) | GB846358A (en) |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2519152A1 (en) * | 1975-04-30 | 1976-11-11 | Ver Flugtechnische Werke | DEVICE FOR STARTING AIRPLANE ENGINES AND OPERATING AIRCRAFT AUXILIARY EQUIPMENT |
DE4106752A1 (en) * | 1990-03-06 | 1991-09-12 | Gen Electric | DEVICE FOR DELIVERING EXHAUST AIR FROM AN AIRPLANE GAS TURBINE ENGINE |
EP0459816A1 (en) * | 1990-06-01 | 1991-12-04 | General Electric Company | Gas turbine engine powered aircraft environmental control system and boundary layer bleed |
US5114103A (en) * | 1990-08-27 | 1992-05-19 | General Electric Company | Aircraft engine electrically powered boundary layer bleed system |
US5137230A (en) * | 1991-06-04 | 1992-08-11 | General Electric Company | Aircraft gas turbine engine bleed air energy recovery apparatus |
US5141182A (en) * | 1990-06-01 | 1992-08-25 | General Electric Company | Gas turbine engine fan duct base pressure drag reduction |
US5143329A (en) * | 1990-06-01 | 1992-09-01 | General Electric Company | Gas turbine engine powered aircraft environmental control system and boundary layer bleed |
US20180038283A1 (en) * | 2015-02-23 | 2018-02-08 | Mitsubishi Heavy Industries Compressor Corporation | Gas turbine starting device and gas turbine system |
GB2566796A (en) * | 2017-07-26 | 2019-03-27 | Unison Ind Llc | Air turbine starter |
Families Citing this family (38)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3010434A (en) * | 1957-07-25 | 1961-11-28 | Rolls Royce | Control mechanism including variable-stroke ram |
GB952982A (en) * | 1959-07-10 | 1964-03-18 | Plessey Co Ltd | Improvements in or relating to composite mechanical constant-speed drives |
US2972911A (en) * | 1959-07-27 | 1961-02-28 | Bendix Corp | Starter and accessory drive |
US3307426A (en) * | 1960-01-11 | 1967-03-07 | Garrett Corp | Constant speed drive starter |
US3115749A (en) * | 1960-06-02 | 1963-12-31 | Plessey Co Ltd | Control valves for reversible air motors |
US3077115A (en) * | 1960-12-07 | 1963-02-12 | Gen Motors Corp | Vehicle drive and starting transmissions |
GB1002940A (en) * | 1961-01-16 | 1965-09-02 | Plessey Co Ltd | Improvements in or relating to constant speed drives |
US3088277A (en) * | 1961-03-07 | 1963-05-07 | Plessey Co Ltd | Control of composite mechanical drives |
US3274855A (en) * | 1962-06-19 | 1966-09-27 | Sundstrand Corp | Starter-drive system |
GB1062631A (en) * | 1963-01-11 | 1967-03-22 | Plessey Uk Ltd | Improvements in or relating to composite hydromechanical constant-speed drives |
DE1274408B (en) * | 1964-01-01 | 1968-08-01 | Plessey Uk Ltd | Combined engine turning and drive device for engine auxiliary systems |
GB1119988A (en) * | 1965-10-14 | 1968-07-17 | Nat Res Dev | Transmission system for interconnecting two rotary machines |
CH425479A (en) * | 1965-10-25 | 1966-11-30 | Saurer Ag Adolph | Auxiliary unit for starting jet engines and for delivering electrical energy |
US3362256A (en) * | 1966-03-01 | 1968-01-09 | Garrett Corp | Combination accessory drive and engine starting mechanism |
US3481220A (en) * | 1968-05-10 | 1969-12-02 | Ford Motor Co | Gearing for a unitary starter-alternator with variable ratio characteristics |
US3521505A (en) * | 1968-07-09 | 1970-07-21 | Garrett Corp | Transmission means |
GB1341961A (en) * | 1970-01-07 | 1973-12-25 | Combined Engineered Products L | Gear drive |
US3861484A (en) * | 1971-02-01 | 1975-01-21 | Kenneth E Joslin | Hybrid vehicular power system |
SE386965B (en) * | 1971-05-21 | 1976-08-23 | R L Bricout | TRANSMISSION WITH AN AUTOMATIC AND CONTINUOUS EXCHANGE RELATIONSHIP |
US4062185A (en) * | 1976-05-13 | 1977-12-13 | General Electric Company | Method and apparatus for windmill starts in gas turbine engines |
US4609842A (en) * | 1984-11-23 | 1986-09-02 | Sundstrand Corporation | In-line constant speed drive and generator |
US5039281A (en) * | 1989-12-26 | 1991-08-13 | General Electric Company | Method and apparatus for supplying compressed air to auxiliary systems of a vehicle |
US5508574A (en) * | 1994-11-23 | 1996-04-16 | Vlock; Alexander | Vehicle transmission system with variable speed drive |
US6851267B2 (en) * | 2002-12-18 | 2005-02-08 | Pratt & Whitney Canada Corp. | Compact quick attach starter-generator installation |
KR101113124B1 (en) * | 2003-02-17 | 2012-02-29 | 인테그랄 파워트레인 리미티드 | Automotive air blowers |
US7251942B2 (en) * | 2004-06-29 | 2007-08-07 | Honeywell International Inc. | Integrated gearless and nonlubricated auxiliary power unit |
GB0415376D0 (en) * | 2004-07-09 | 2004-08-11 | Rolls Royce Plc | A turbine engine arrangement |
WO2006121045A1 (en) * | 2005-05-10 | 2006-11-16 | Komatsu Ltd. | Generator/motor mounted on engine |
NZ584737A (en) * | 2007-09-28 | 2012-12-21 | Vrt Innovations Ltd | A variable transmission with modulation means for continuous variation of the output relative to the input |
FR2938015B1 (en) * | 2008-11-05 | 2015-05-29 | Snecma | ATTENUATION OF TORQUE PICS ON A GEAR TRAIN IN A TURBOMACHINE |
IT201600071644A1 (en) * | 2016-07-08 | 2018-01-08 | Nuovo Pignone Tecnologie Srl | VARIABLE SPEED TRANSMISSION WITH AUXILIARY DRIVE AND SYSTEM THAT USES IT |
US10767564B2 (en) * | 2017-03-17 | 2020-09-08 | Hamilton Sunstrand Corporation | Air turbine starter with automated variable inlet vanes |
US20190032569A1 (en) * | 2017-07-26 | 2019-01-31 | Unison Industries, Llc | Air turbine starter |
US20190032566A1 (en) * | 2017-07-26 | 2019-01-31 | Unison Industries, Llc | Air turbine starter |
DE102018207001B4 (en) * | 2018-05-07 | 2021-07-01 | Hanon Systems Efp Deutschland Gmbh | Fluid pumping system |
DE102018211799B4 (en) * | 2018-07-16 | 2021-05-12 | Hanon Systems Efp Deutschland Gmbh | Pump arrangement for a motor vehicle |
US11408353B2 (en) | 2019-03-28 | 2022-08-09 | Honeywell International Inc. | Auxiliary power unit with plural spool assembly and starter transmission arrangement |
US20230365268A1 (en) * | 2022-05-11 | 2023-11-16 | Parallel Flight Technologies, Inc. | Power module and clutch mechanism for unmanned aircraft systems |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE351467A (en) * | 1927-07-05 | |||
DE738877C (en) * | 1936-10-09 | 1943-09-10 | Daimler Benz Ag | Method for starting internal combustion engines, especially those for aircraft |
DE760782C (en) * | 1941-07-22 | 1955-06-10 | Bosch Gmbh Robert | Method for starting internal combustion engines |
US2582848A (en) * | 1942-03-06 | 1952-01-15 | Lockheed Aircraft Corp | Aircraft power plant and cabin pressurizing system |
US2402547A (en) * | 1942-05-08 | 1946-06-25 | Chrysler Corp | Combined starter and generator drive |
DE922870C (en) * | 1945-04-19 | 1955-01-27 | Siemens Ag | Gas turbine plant working with constant pressure combustion |
US2485126A (en) * | 1947-01-10 | 1949-10-18 | Garrett Corp | Hydraulically controlled variablespeed transmission |
DE954481C (en) * | 1950-08-23 | 1956-12-20 | Gyreacta Transmissions Ltd | Drive system for vehicles with front and rear wheel drive |
US2693080A (en) * | 1950-09-13 | 1954-11-02 | Turbex Corp | Differential gas turbine |
US2740303A (en) * | 1951-02-14 | 1956-04-03 | Gen Motors Corp | Heavy duty drive gearing and control system |
FR1035811A (en) * | 1951-04-10 | 1953-08-31 | Air Equipement | Improvements in the supply of fuel to combustion engines, in particular those comprising a continuous supply of compressed combustion air |
DE949699C (en) * | 1952-07-09 | 1956-09-27 | Sigmund Gundling | Internal combustion piston engine with exhaust gas turbine |
FR1107114A (en) * | 1953-05-19 | 1955-12-28 | Rolls Royce | Gas turbine |
GB817591A (en) * | 1954-11-08 | 1959-08-06 | Parsons C A & Co Ltd | Improvements in and relating to gas turbine plants |
DE1031058B (en) * | 1955-06-22 | 1958-05-29 | Bristol Aero Engines Ltd | Propeller-driving gas turbine |
DE1161142B (en) * | 1956-09-28 | 1964-01-09 | Garrett Corp | Overspeed protection for turbines |
-
1957
- 1957-06-12 US US665147A patent/US2908189A/en not_active Expired - Lifetime
-
1958
- 1958-06-11 GB GB18701/58A patent/GB846358A/en not_active Expired
- 1958-06-12 DE DE19581401273D patent/DE1401273B1/en active Pending
- 1958-06-12 FR FR1208466D patent/FR1208466A/en not_active Expired
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2519152A1 (en) * | 1975-04-30 | 1976-11-11 | Ver Flugtechnische Werke | DEVICE FOR STARTING AIRPLANE ENGINES AND OPERATING AIRCRAFT AUXILIARY EQUIPMENT |
DE4106752A1 (en) * | 1990-03-06 | 1991-09-12 | Gen Electric | DEVICE FOR DELIVERING EXHAUST AIR FROM AN AIRPLANE GAS TURBINE ENGINE |
EP0459816A1 (en) * | 1990-06-01 | 1991-12-04 | General Electric Company | Gas turbine engine powered aircraft environmental control system and boundary layer bleed |
US5125597A (en) * | 1990-06-01 | 1992-06-30 | General Electric Company | Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system |
US5141182A (en) * | 1990-06-01 | 1992-08-25 | General Electric Company | Gas turbine engine fan duct base pressure drag reduction |
US5143329A (en) * | 1990-06-01 | 1992-09-01 | General Electric Company | Gas turbine engine powered aircraft environmental control system and boundary layer bleed |
US5114103A (en) * | 1990-08-27 | 1992-05-19 | General Electric Company | Aircraft engine electrically powered boundary layer bleed system |
US5137230A (en) * | 1991-06-04 | 1992-08-11 | General Electric Company | Aircraft gas turbine engine bleed air energy recovery apparatus |
US20180038283A1 (en) * | 2015-02-23 | 2018-02-08 | Mitsubishi Heavy Industries Compressor Corporation | Gas turbine starting device and gas turbine system |
US10760497B2 (en) * | 2015-02-23 | 2020-09-01 | Mitsubishi Heavy Industries Compressor Corporation | Gas turbine starting device and gas turbine system |
GB2566796A (en) * | 2017-07-26 | 2019-03-27 | Unison Ind Llc | Air turbine starter |
Also Published As
Publication number | Publication date |
---|---|
DE1401273B1 (en) | 1970-03-26 |
FR1208466A (en) | 1960-02-24 |
US2908189A (en) | 1959-10-13 |
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